# Service difficulty reports: N425FE, cancelled Feb 18, 2016

A list on [N425FE, cancelled Feb 18, 2016](https://openairdocs.org/deregistered/N425FE-2016-02-18.md).

Matched to this aircraft by N-number and event date, checked against the reported serial number, make and model. Newest first.

Page 1 of 7 · 303 reports

- [SDR FDEA201203130922](https://openairdocs.org/sdr/FDEA201203130922.md): Handle · dirty · Mar 13, 2012 · N425FE · Airbus A310203 · Trailing Edge Flap Control System
  > FLAP/SLAT HANDLE FAILED TO MOVE PAST 15/0 SETTING ON RETRACTION AND 20/20 SETTING ON LANDING. T/S SFCC FAULTED SUPPLY PSW. PARTS ID ARE FOR T/S, ADDITIONAL PARTS MAY BE REQUIRED. HIGH PRESS SW. REMOVED FLAP/SLAT HANDLE, CLEANED SPRING AND RE-ASSEMBLE. OP
- [SDR FDEA201202070508](https://openairdocs.org/sdr/FDEA201202070508.md): Pin · misinstalled · Feb 7, 2012 · N425FE · Airbus A310203 · Trailing Edge Flap Control System
  > AFTER TAKEOFF, FLAP LEVER WOULD NOT RETRACT BEYOND 15/0 POSITION. LEVER WOULD NOT DROP DOWN INTO GATE. SLAT/FLAP POSITION REMAINED AT 15/15. ON APPROACH, FLAPS CAME TO 20/20, BUT LEVER WOULD NOT GO INTO 30/40 POSITION. CHECKED UNDER CENTER PEDESTAL FOR DE
- [SDR FDEA201201130164](https://openairdocs.org/sdr/FDEA201201130164.md): Skin · failed · Jan 13, 2012 · N425FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > R1 DOOR AFT EXTERNAL SKIN PANEL REQUIRES REMOVAL TO SUPPORT FRAME 16A REPAIR. SKIN PANEL TO BE REPLACED AFTER FRAME 16A REPAIR. R & R R1 AFT EXTERNAL SKIN PANEL IAW SRM 51-72-10, 51-40-21 AND 51-40-44.
- [SDR FDEA201201110098](https://openairdocs.org/sdr/FDEA201201110098.md): Failsafe · failed · Jan 11, 2012 · N425FE · Airbus A310203 · Fuselage Main, Structure
  > R1 DOOR FAILSAFE RING REQUIRES REMOVAL TO FOM FARME 16A RT FRAME REPAIR. REMOVED FAIL SAFE RING IAW SRM 51-40-21 AND EA 6-5310-135257B. LOCATED AND DRILLED NEW FAIL SAFE RING AT R1 DOOR IAW DWG 12R53610899 AND SRM 51-40-44. INSTALLED NEW FAIL SAFE RING AT R1
- [SDR FDEA201201050027](https://openairdocs.org/sdr/FDEA201201050027.md): Frame · damaged · Jan 5, 2012 · N425FE · Airbus A310203 · Fuselage Main, Frame
  > FRAME 16A RT DAMAED. REMOVED FRAME IAW SRM 51-40-21, PG 1 AND EA 6-5310-135257B. LOCATED AND DRILLED NEW FRAME IAW SRM 51-40-44, PG 9. INSTALLED NEW FRAME IAW SRM 51-40-21, PG 19 AND EA 6-5310-135257B, STEP 18, PG 4.
- [SDR FDEA201201050026](https://openairdocs.org/sdr/FDEA201201050026.md): Depressor · damaged · Jan 5, 2012 · N425FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > R1 DOOR FRAME 16A SEAL DEPRESSOR DAMAGED FRAME 16A. REPAIR REMOVED SEAL DEPRESSOR IAW SRM 51-72-10. LOCATED AND DRILLED NEW SEAL DEPRESSOR IAW A310 51-40-44. INSTALLED NEW SEAL DEPRESSOR IAW SRM 51-40-21 AND 51-72-10.
- [SDR FDEA201107012552](https://openairdocs.org/sdr/FDEA201107012552.md): Computer · malfunctioned · Jul 1, 2011 · N425FE · Airbus A310203 · Auto Throttle System
  > REJECTED TAKEOFF AT APPROX 78 KTS. NR1 ENGINE EXCEEDED THE SELECTED FLEX POWER SETTING N1(101.4). THE NR2 ENGINE ENGINE MOMENTARITLY STABLIZED AT 101.4 N1 THEN INCRESED UNSYMETERICALLY TO THRUST LIMIT OFF 107.1. CLEARED RUNWAY AND CHECKED ALL GUAGES FOR EXCE
- [SDR FDEA201012304784](https://openairdocs.org/sdr/FDEA201012304784.md): Switch · inoperative · Dec 30, 2010 · N425FE · Airbus A310203 · Door Warning System
  > ECAM, FWD CARGO DOOR NOT CLOSED CAME ON AT FL 220 ON DEPARTURE, RAN QRH, CABIN ALT OK, RETURNED TO DEPARTURE, FWD CARGO SWITCH FAULT ECAM CAME ON LATER. R & R FWD CARGO DOOR SWITCH (16WS) IAW MM 52-71-11-04.
- [SDR FDEA201009173534](https://openairdocs.org/sdr/FDEA201009173534.md): Skin · damaged · Sep 17, 2010 · N425FE · Airbus A310203 · Trailing Edge Flaps
  > LEFT WING OTBD FLAP LOWER SKIN DISBONDED 7.5 IN LENGTH X 1.5 IN WIDE AT T/E,48 IN INBD FROM OTBD EDGE. REPAIRED LT WING T/E SKIN IAW EA 6-5750-135278 - WINGS - LT OTBD FLAP T/E -REPAIR TRACKING EA.
- [SDR FDEA201009163513](https://openairdocs.org/sdr/FDEA201009163513.md): Seat Track · bent · Sep 16, 2010 · N425FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > SEAT TRACK SCALLOP 9 INCHES AFT OF FRAME 60 THE LOCKING TABS ARE CUT OUT AND 6 INCHES AFT OF FR60 THE LOCKING TABS ARE BENT UP. DAMAGED SEAT TRACK SCALLOPS WERE REPAIRED BY CUTTING SEAT TRACK AND REPAIRED SEAT TRACK IAW SRM 53-10-16, FIG 201, PAGE 206.
- [SDR FDEA201009153424](https://openairdocs.org/sdr/FDEA201009153424.md): Skin · misrepaired · Sep 15, 2010 · N425FE · Airbus A310203 · Trailing Edge Flaps
  > PREVIOUS EXTERNAL REPAIR DOUBLER LOCATED ON LT WING INBD FLAP UPPER SKIN AT RIB 10 TO 11 AND BETWEEEN THE REAR SPAR AND AUXILIARY SPAR ON STRINGERS 6 AND 7 MEASURES 5.4 IN X 6.6 IN. PREVIOUSLY INSTALLED REPAIR LOCATED AT LT WING INBD FLAP UPPER MAIN SKIN AT R
- [SDR FDEA201009153423](https://openairdocs.org/sdr/FDEA201009153423.md): Frame · failed · Sep 15, 2010 · N425FE · Airbus A310203 · Fuselage Main, Frame
  > PREVIOUS FRAME REPAIR LOCATED IN BULK CARGO COMPARTMENT UNDEFLOOR ON FRAME 67 BETWEEN STRINGERS 43 TO 46 RT HAS A REPAIR AGLE ON AFT SIDE OUTER FLANGE MEASURING 9-8 IN LONG. PREVIOUSLY INSTALLED REPAIR LOCATED IN BULK CARGO ON FRAME 67 BETWEEN STRINGERS 43 TO
- [SDR FDEA201009113346](https://openairdocs.org/sdr/FDEA201009113346.md): Skin · dented · Sep 11, 2010 · N425FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > L 2 DOOR EXTERIOR SKIN 20.5 INCHES FROM AFT END OF DOOR SKIN,12.5 INCHES FROM BOTTOM OF DOOR SKIN HAS SM DENT,10 MM W X.014 IN DEEP CUT OUT DAMAGED SECTION OF EXTERIOR DOOR SKIN AT FR 75 BETWEEN STR 24 LT AND STR 25 LT AND INSTALLED REPAIR EXTERNAL DOUBLER
- [SDR FDEA201009113345](https://openairdocs.org/sdr/FDEA201009113345.md): Cargo Track · cracked · Sep 11, 2010 · N425FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > MAIN CARGO DECK FLOOR SUPPORT STRUCTURE FR 54.2 RT SIDE NR 5 SEAT TRACK HAS 3.5 INCH CRACK ON LOWER PART OF SEAT TRACK. REMOVED DAMAGED TRACK SECTION BETWEEN FR 54.2 AND FR 55/58 AND INSTALLED NEW REPLACEMENT TRACK SECTION AT TRACK NR5 RT IAW SRM 51-75-10,53
- [SDR FDEA201009033253](https://openairdocs.org/sdr/FDEA201009033253.md): Stringer · corroded · Sep 3, 2010 · N425FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > IN FWD CARGO AT FRONT FACE OF PRESSURE BULKHEAD FR 39 ALL THE WAY TO BOTTOM AND 24 " LT OF BOTTOM CTR THERE IS CORROSION APPROX 8 SQ INCHES AT STRINGER 50L. REMOVED CORROSION AND DAMAGED AREA IAW SRM 53-15-17 PG 215-216. REPAIRED AREA BY INSTALLING 1 EA DOUB
- [SDR FDEA201009023250](https://openairdocs.org/sdr/FDEA201009023250.md): Beam · corroded · Sep 2, 2010 · N425FE · Airbus A310203 · Fuselage Main, Structure
  > LONGITUDENAL BEAM Y953 BETWEEN FR 12A AND FR 14 HAS EXFOLIATION CORROSION IN THE MAIN DECK. REMOVED CORROSION IAW SRM 51-74-10, CHECKED, FOUND OUT OF LIMIT. FABRICATED NEW TEE CAP AND REPAIRED IAW SRM 53-12-15 AND DWG 12A536-10797.
- [SDR FDEA201009023249](https://openairdocs.org/sdr/FDEA201009023249.md): Floorbeam · cracked · Sep 2, 2010 · N425FE · Airbus A310203 · Fuselage Main, Floor Beam
  > IN FWD CARGO MAIN DECK FLOORBEAM (FR 37) AT 27 INCHES RT OF CTR LINE. FWD FACE IS A CRACK IN THE UPPER SIDE OF THE BEAM APPROX.7500 INCH LONG REMOVED DAMAGE SECTION, INSTALLED NEW BEAM SECTION IAW SRM 53-10-15, FIG 201.
- [SDR FDEA201008303199](https://openairdocs.org/sdr/FDEA201008303199.md): Floor Support · corroded · Aug 30, 2010 · N425FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > MAIN DECK CARGO COMPT 10 IN AFT OF FR 14, 57 IN. LT OF CTR LINE FLOOR SUPPORT CHANNEL HAS 4 SQ IN OF LEVEL 1 CORROSION ON UPPER SURFACE OF CHANNEL. REMOVED LEVEL 1 CORROSION. DURING CORROSION REMOVAL FOUND FLOOR SUPPORT CHANNEL OUT OF LIMITS. R & R FLOOR S
- [SDR FDEA201008283167](https://openairdocs.org/sdr/FDEA201008283167.md): Seat Track · damaged · Aug 28, 2010 · N425FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > MAIN FLOOR SUPPORT FLANGE UPPER SURFACE OF SEAT TRACK GOUGED.5 SQ IN. LOCATED 4 IN FWD OF FR 17 AND 37IN RT OF CTR LINE. BLENDED GOUGE IN MAIN FLOOR SUPPORT FLANGE 4IN FWD OF FR17 AND37IN RT OF CTR LINE IAW SRM 51-74-10. CHECK LIMITS FOUND OUT OF LIMIT I
- [SDR FDEA201008273165](https://openairdocs.org/sdr/FDEA201008273165.md): Floor Support · corroded · Aug 27, 2010 · N425FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > MAIN DECK CARGO COMPARTMENT 10 IN AFT OF FR 14, 53 IN LT OF C/L FLOOR CHANNEL SUPPORT FOR COURIER SEAT HAS 3 SQ IN OF CORROSION AROUND ANCHOR NUTPLATES TOP SURFACE. REMOVED LEVEL 1 CORROSION. REMOVED DAMAGED FLOOR SUPPORT (WEB) AND REPLACED WITH NEW PART BE
- [SDR FDEA201008273164](https://openairdocs.org/sdr/FDEA201008273164.md): Floor Support · corroded · Aug 27, 2010 · N425FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > MAIN DECK CARGO COMPARTMENT 5 IN AFT OF FR 14, 31 IN LT OF C/L FLOOR SUPPORT UPPER SURFACE HAS 3 SQ IN OF CORROSION. REMOVED LEVEL 1 CORROSION REMOVED DAMAGED FLOOR SUPPORT, FABRICATED REPLACEMENT PART AND INSTALLED NEW PART BETWEEN FR11 AND FR 15, AT Y770
- [SDR FDEA201008263154](https://openairdocs.org/sdr/FDEA201008263154.md): Floorbeam · cracked · Aug 26, 2010 · N425FE · Airbus A310203 · Fuselage Main, Floor Beam
  > MAIN CARGO DECK FLOOR STRUCTURE FR 54.3 BETWEEN SEAT TRACKS 2R AND 3R HAS 1 EA,.25 " CRACK IN STRUCTURE CROSSBEAM. CUT OUT DAMAGED AREA OF CROSSBEAM IAW SRM 53-10-15, FIG 204. NDT VERIFIED CRACKED AREA. REMOVED IAW NTM 51-10-08. FABBED REPAIR PART AND INST
- [SDR FDEA201008263153](https://openairdocs.org/sdr/FDEA201008263153.md): Seat Track · corroded · Aug 26, 2010 · N425FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > UPPER DECK FLOOR STRUCTURE BETWEEN FR 18 AND FR19 AT SEATTRACK 2L (Y450) HAS LEVEL 1 CORROSION ON FLANGE UPPER SURFACE APPROX 6 SQ. INCHES, TOTAL CORROSION WAS REMOVED IAW SRM 51-74 10. CHECKED LIMITS AND FOUND TO BE OUT OF LIMITS IAW SRM 53-10-16. R & R SEAT
- [SDR FDEA201008263152](https://openairdocs.org/sdr/FDEA201008263152.md): Seat Track · damaged · Aug 26, 2010 · N425FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > MAIN CARGO DECK FLOOR STRUCTURE FRAME 54.2 SEAT TRACK STRUCTURE 3R HAS 1 EA.1875" DRILL START (MISDRILL). R & R SEAT TRACK 3R IAW SRM 51-72-10 ON MAIN DECK FLOOR STRUCTURE FR54 TO FR 54.2
- [SDR FDEA201008253135](https://openairdocs.org/sdr/FDEA201008253135.md): Floor Support · misrepaired · Aug 25, 2010 · N425FE · Airbus A310203 · Fuselage Miscellaneous Structure
  > PREVIOUS REPAIR LOCATED ON MAIN CABIN COURIER AREA FLOOR SUPPORT "T" CAP LONGERON RT SIDE BETWEEN FRAMES 12A TO 14, NR5 RT LONGERON FROM CTR- Y1959, HAS 2 EA REPAIR ANGLES MEASURING 11.4" LONG EACH AND 1 EA REPAIR SECTION MEASURING 35" LONG FROM FRAME 12A T
- [SDR FDEA201008253133](https://openairdocs.org/sdr/FDEA201008253133.md): Stringer · misrepaired · Aug 25, 2010 · N425FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > PREVIOUS STRINGER REPAIR LOCATED IN AFT CABIN UNDER FLOOR BEHIND BULK CARGO ON STRINGER 39 LT BETWEEN FRAMES 73 TO 74, HAS 1 EACH REPAIR ANGLE SPLICE 12.6" LONG WITH A STRINGER CUTOUT OF 4.4" LONG. PREVIOUSLY INSTALLED REPAIR LOCATED AT AFT CABIN UNDERFLOOR B
- [SDR FDEA201008253132](https://openairdocs.org/sdr/FDEA201008253132.md): Skin · misrepaired · Aug 25, 2010 · N425FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > PREVIOUS EXTERNAL LAP SEAM REPAIR LOCATED AT LT SIDE FUSELAGE SKIN AT FRAME 38 AND BETWEEN STRINGERS 42 TO 45 LT. THE REPAIR FILLER MEASURES 8.6" X 23.5" AND THE REPAIR DOUBLER MEASURES 21.9" X 10.5". PREVIOUSLY INSTALLED REPAIR LOCATED AT LT SIDE FUSELAGE S
- [SDR FDEA201008223089](https://openairdocs.org/sdr/FDEA201008223089.md): Skin · dented · Aug 22, 2010 · N425FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > EXTERIOR SKIN JUST AFT OF AFT CARGO DOOR BETWEEN FRAMES 64 AND 65 AND STR 39R AND 44R HAS MULTIPLE DENTS. DEEPEST DENT MEASURED APROX.7500 IN WIDE,1IN LONG AND.027IN DEEP. NDT CHECK C/W NO CRACKS FOUND IAW NTM 51-10-08. REPAIRED EXTERIOR SKIN BY FABRICATI
- [SDR FDEA201008213078](https://openairdocs.org/sdr/FDEA201008213078.md): Skin · misrepaired · Aug 21, 2010 · N425FE · Airbus A310203 · Leading Edge Devices
  > PREVIOUS FLUSH REPAIR LOCATED ON LT WING NR 2 SLAT NOSE SKIN BETWEEN RIB 13 AND 15 JUST BELOW UPPER GIRDER MEASURES 5.4 X 5.8 INCH PREVIOUS REPAIR WAS DETERMINED NOT TO BE IAW SRM 57-43-11, FIG 202, SHEET 3, PAGES 209 TO 213 AND PAGE 216 DUE TO 64 EA BLIND FAS
- [SDR FDEA201008213077](https://openairdocs.org/sdr/FDEA201008213077.md): Stringer · misrepaired · Aug 21, 2010 · N425FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 47 LT BETWEEN FR 59 AND FR 60 HAS 1EA STRINGER REPAIR SECTION FROM FR 55/58 TO 60 MEASURING 29.4IN LONG AND 1EA REPAIR SPLICE 7.9 INCH LONG. PREVIOUS REPAIR WAS DETERMINED NOT TO BE IAW SRM 53-10-14, FI
- [SDR FDEA201008213076](https://openairdocs.org/sdr/FDEA201008213076.md): Stringer · misrepaired · Aug 21, 2010 · N425FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 45 LT BETWEEN FR 60 AND FR 61 HAS 1 EA STRINGER REPAIR SECTION FROM FR 55/58 TO 62 MEASURING 51IN LONG AND 1EA REPAIR SPLICE 8IN LONG. PREVIOUS REPAIR WAS DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201,
- [SDR FDEA201008213075](https://openairdocs.org/sdr/FDEA201008213075.md): Stringer · misrepaired · Aug 21, 2010 · N425FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > PREVIOUS STR REPAIR LOCATED IN AFT CARGO ON STRINGER 52 LT BETWEEN FRAMES 62 TO 63 HAS 1 EACH STRINGER REPAIR SECTION FROM FR 60 TO 63 MEASURING 43IN LONG AND 1EA REPAIR SPLICE 7.6 IN LONG. PREVIOUS REPAIR WAS DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201,
- [SDR FDEA201008203074](https://openairdocs.org/sdr/FDEA201008203074.md): Stringer · misrepaired · Aug 20, 2010 · N425FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > PREVIOUS STR REPAIR LOCATED IN AFT CARGO ON STR 46 LT BETWEEN FRAMES 61 TO 62 HAS 1EA STR SECTION FROM FR 55/58 TO 62 MEASURING 71.7 INCH LONG AND 1EA REPAIR SPLICE 7.9 INCH LONG. PREVIOUS REPAIR WAS DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201, PAGES 203
- [SDR FDEA201008203073](https://openairdocs.org/sdr/FDEA201008203073.md): Stringer · misrepaired · Aug 20, 2010 · N425FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > PREVIOUS STR REPAIR LOCATED IN BULK CARGO ON STR 54 R BETWEEN FR 66 AND FR67 HAS 1 EA STR REPAIR SECTION FROM FR 65 TO FR 67 MEASURING 32 IN LONG AND 1EA REPAIR SPLICE 8.1 INCH LONG PREVIOUS INSTALLED REPAIR WAS DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201
- [SDR FDEA201008203072](https://openairdocs.org/sdr/FDEA201008203072.md): Stringer · misrepaired · Aug 20, 2010 · N425FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 55 R/H BETWEEN FR66 AND FR67 HAS 1 EACH STRINGER REPAIR SECTION FROM FR 65 TO 67 MEASURING 32 INCH LONG AND 1 EACH REPAIR SPLICE 8.1 INCH LONG. PREVIOUS REPAIR WAS DETERMINED NOT TO BE IAW SRM 53-1
- [SDR FDEA201008203071](https://openairdocs.org/sdr/FDEA201008203071.md): Stringer · misrepaired · Aug 20, 2010 · N425FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > PREVIOUS STRINGER REPAIR LOCATED IN BULK CARGO ON STRINGER 56 LT BETWEEN FRAMES 66 TO 67 HAS 1 EA STRINGER REPAIR SECTION FROM FR 65 TO 67 MEASURING 33.5 INCH LONG AND 1 EACH REPAIR SPLICE 8.2 INCH LONG PREVIOUSLY INSTALLED REPAIR WAS DETERMINED NOT TO BE IA
- [SDR FDEA201008203070](https://openairdocs.org/sdr/FDEA201008203070.md): Seat Track · misrepaired · Aug 20, 2010 · N425FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > PREVIOUS REPAIR LOCATED ON MAIN CABIN SEAT TRACK NR1 Y0 BETWEEN FRAMES 61 TO 62, HAS 1 EA REPAIR ANGLE ON LT SIDE UPPER FLANGE MEASURING 9.3 INCHES LONG X 1.7 IN TALL AND 1 EA UPPER FLANGE REPAIR FILLER FOR CUT MEASURING 3.1 INCHX 0.900 IN PREVIOUSLY INSTALLED
- [SDR FDEA201008203069](https://openairdocs.org/sdr/FDEA201008203069.md): Stringer · misrepaired · Aug 20, 2010 · N425FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > PREVIOUS STRINGER REPAIR LOCATED IN FWD CARGO ON STR 46 RT BETWEEN FRAME 38 AND FR 38.1 HAS 1 EACH REPAIR SPLICE 6.8 INCH LONG AND THE STRINGER SECTION WAS CUT ONLY FOR ACCESS ORIGINAL STRINGER INSTALLED PREVIOUSLY INSTALLED REPAIR DETERMINED TO NOT IAW S
- [SDR FDEA201008203068](https://openairdocs.org/sdr/FDEA201008203068.md): Stringer · misrepaired · Aug 20, 2010 · N425FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > PREVIOUS STRINGER REPAIR LOCATED IN FWD CARGO ON STR 47 RT BOTTOM FRAMES 38 AND FR 38.1 HAS 1 EACH REPAIR SPLICE 6.9 INCH LONG AND THE STRINGER SECTION WAS CUT ONLY TO REMOVE FOR ACCESS, ORIGINAL STRINGER INSTALLED. PREVIOUS REPAIR DETERMINED NOT TO BE IAW S
- [SDR FDEA201008203065](https://openairdocs.org/sdr/FDEA201008203065.md): Stringer · misrepaired · Aug 20, 2010 · N425FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > PREVIOUS STRINGER REPAIR IN FWD CARGO ON STR 45 RT BETWEEN FR 38 AND FR 38.1 HAS 1 EACH REPAIR SPLICE 6.8 INCH LONG AND THE STR SECTION WAS CUT ONLY TO REMOVE FOR ACCESS ORIGINAL STR INSTALLED PREVIOUS REPAIR DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201 ON
- [SDR FDEA201008203064](https://openairdocs.org/sdr/FDEA201008203064.md): Stringer · misrepaired · Aug 20, 2010 · N425FE · Airbus A310203 · Fuselage Main, Longeron/Stringer
  > PREVIOUS STRINGER REPAIR LOCATED IN AFT CARGO ON STRINGER 51 RT BETWEEN FRAMES 60 TO 62 HAS 1 EA, STRINGER REPAIR SECTION MEASURING 15.1 INCH LONG AND 2 EA. REPAIRS SPLICES 8.1 INCH LONG PREVIOUSLY REPAIRS DETERMINED NOT TO BE IAW SRM 53-10-14, FIG 201, DUE T
- [SDR FDEA201008163008](https://openairdocs.org/sdr/FDEA201008163008.md): Skin · misrepaired · Aug 16, 2010 · N425FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > PREVIOUS EXTERNAL LAP SEAM REPAIR LOCATED AT LOWER FUSELAGE SKIN AT FRAME 66 AND BETWEEN STRINGERS 54 LT TO 56 RT. THE REPAIR FILLER MEASURES 19.3 IN X 11 IN AND THE REPAIR DOUBLER MEASURES 17.5 IN X 12.9 IN. AGING ACFT. PREVIOUSLY INSTALLED REPAIR LOCATED AT
- [SDR FDEA201008122943](https://openairdocs.org/sdr/FDEA201008122943.md): Seat Track · damaged · Aug 12, 2010 · N425FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > MDCC SEAT TRACK 4L HAS 2 LOCK TABS GOUGED AT FRAMES 54.3-55. BLENDED GOUGES ON SEAT TRACK IAW SRM 51-74-10. CHECKED LIMITS IAW SRM 53-10-16, FIG 101 AND FOUND OUT OF LIMITS. R & R SEAT TRACK 4L BETWEEN FRAMES 54.3 AND 55 IAW SRM 51-40-21.
- [SDR FDEA201008112937](https://openairdocs.org/sdr/FDEA201008112937.md): Seat Track · corroded · Aug 11, 2010 · N425FE · Airbus A310203 · Fuselage, Seat/Cargo Attach Fittings
  > MAIN DECK CARGO COMPARTMENT SEAT TRACK 4 LT HAS 3 EA AREAS OF CORROSION ON SCALLOPS AND FLANGE, ABOUT 30 SQ IN BETWEEN FR 74 AND FR 76. REMOVED LEVEL 1 CORROSION. REMOVED DAMAGED SECTION OF TRACK, FABRICATED REPLACEMENT SECTION OF SEAT TRACK, 4 LT BETWEEN
- [SDR 08FDEA04423](https://openairdocs.org/sdr/08FDEA04423.md): Unknown · unknown · Oct 11, 2008 · N425FE · Airbus A310203 · Aircraft Fuel System
  > LO TANK READ 1200 LBS LESS AFTER 1 HR T/O. GAUGE HAD DASH IN LAST DIGIT. DASH WENT AWAY. FQI CONTINUED TO DECREASE TO 1200 TOTAL. ON DESCENT FUEL INCREASED, AT LDG FQI READ OK. RELEASE FOR SVC/MEL 28-42-01-01 CAT: C EXP: 21OCT08 ALL LO TANK IND INOP. FUE
- [SDR 08FDEA03275](https://openairdocs.org/sdr/08FDEA03275.md): Connector · inoperative · Aug 6, 2008 · N425FE · Airbus A310203 · Fire Protection System Wiring
  > AFTER T/O FROM KIND, NR 2 ENG SHOWED ADVISORY FRO "NAC HEAT" OF 90. LEVELED OFF AT 15,000 FEET AND SLOWED TO 200 K. NAC HEAT DID NOT REDUCE. CONSULTED GOC AND RETURNED TO KIND AS EMERGENCY A/C. FIRE DEPT FOUND NO HOTSPOTS. SINGLE-ENG TAXIED TO PARKING. CR
- [SDR 08FDEA01560](https://openairdocs.org/sdr/08FDEA01560.md): Skin · damaged · Apr 25, 2008 · N425FE · Airbus A310203 · Fuselage Main, Plate/Skin
  > FOUND 5 HOLES AT FRAME 16A TO HAVE PRE EXISTING TOOLING DAMAGE IN HOLES, FASTENERS MARKED AS A, B, C, D,AND E. COMPLIED WITH EA NR 6-5310-118477 TITLE: " FUSELAGE, AD 2007-11-12 5653-2037-SKIN AT FRAME 16A, OVERSIZED FASTENERS HOLES ".
- [SDR 08FDEA01467](https://openairdocs.org/sdr/08FDEA01467.md): Skin · damaged · Apr 21, 2008 · N425FE · Airbus A310203 · Elevator, Plate/Skin
  > RIGHT ELEVATOR UPPER SURFACE TRAILING EDGE; INBD SECTION HAD 2 DENTS AND A PUNCTURE ON THE INBD T/E WEDGE. REPAIRED DAMAGE TO RT ELEVATOR UPPER SURFACE BY, REMOVING DAMAGED AREAS AND FABBED AND BONDING CORE, AND APPLYING FIBERGLASS LAYUPS IAW A310SRM 55-21-11
- [SDR 08FDEA01445](https://openairdocs.org/sdr/08FDEA01445.md): Attach Angle · cracked · Apr 17, 2008 · N425FE · Airbus A310203 · Wing, Attach Fittings
  > LEFT WING ATTACHING ANGLE FOR L/E PANEL 523 HB IS CRACKED. FABRICATED A NEW REINFORCING PLATE IAW AIRBUS DWG 23-A-572-43292 ISSUE F. PRIMED IAW A310 SRM 51-21-10 AND 51-23-10. REPLACED REINFORCING PLATE IAW A310 SRM 51-40-21.
- [SDR 08FDEA01421](https://openairdocs.org/sdr/08FDEA01421.md): Door Frame · gouged · Apr 16, 2008 · N425FE · Airbus A310 · Cargo/Baggage Doors
  > AFT PIT DOOR, LWR FWD CORNER, GOUGED. FOUND GOUGE TO BE OUT OF LIMITS IAW SRM 51-10-00. REMOVED AND REPLACED EDGE SECTION IAW SRM 51-40-21. FOR ADJUSTMENT AND CHECK SEE WC 41X5114ALI.

Next page: https://openairdocs.org/deregistered/N425FE-2016-02-18/reports.md?page=2

## The whole list in SQL

Runs in DuckDB 1.2 or later on the release's Parquet files over HTTPS:

```sql
SELECT sdr_id, difficulty_date, n_number, aircraft_make, aircraft_model, part_name, part_condition, jasc_code, discrepancy
FROM 'https://openairdocs.org/data/latest/faa_service_difficulty_report.parquet'
WHERE n_number = 'N425FE' AND deregistration_id = 'N425FE-2016-02-18'
ORDER BY difficulty_date DESC
```

This list as a web page: https://openairdocs.org/deregistered/N425FE-2016-02-18/reports

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